CN110701111A - Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane - Google Patents
Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane Download PDFInfo
- Publication number
- CN110701111A CN110701111A CN201911024721.5A CN201911024721A CN110701111A CN 110701111 A CN110701111 A CN 110701111A CN 201911024721 A CN201911024721 A CN 201911024721A CN 110701111 A CN110701111 A CN 110701111A
- Authority
- CN
- China
- Prior art keywords
- blade
- splitter
- guide
- vane
- pressure loss
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
Abstract
The invention discloses a method for reducing total pressure loss of a guide vane of an axial flow fan by using a splitter vane, wherein the splitter vane parallel to the guide vane is arranged between the circumferential distances of the guide vane; the splitter blade is positioned at the blade root of the guide blade and connected with a hub of the axial flow fan; the chord length of the splitter blade is 50% of that of the guide blade, and the height of the splitter blade is smaller than 10% of that of the guide blade. The mounting angle of the splitter blade should be greater than that of the guide vane, and the difference between the mounting angles of the splitter blade and the guide vane should be less than 10 degrees. The distance between the splitter blade and the root of the guide blade close to the splitter blade is 30 mm. The invention can reduce the generation of secondary airflow by utilizing the splitter blade, and can reduce the aggregation of airflow in the included angle area between the root part of the guide blade and the end wall surface, thereby finally achieving the purposes of reducing the total pressure loss of the guide blade and improving the working efficiency of the axial flow fan.
Description
Technical Field
The invention belongs to the technical field of axial flow fans, and particularly relates to a method for reducing total pressure loss of a guide vane of an axial flow fan by using a splitter vane.
Background
Axial fans typically consist of a casing, a motor, an impeller, and guide vanes, which are typically located behind the impeller. In the use process of the axial flow fan, the impeller can generate deflection airflow, and the guide vanes are used for rotating the deflection airflow back to the axial direction so as to achieve the purpose of improving the working efficiency of the axial flow fan.
The prior art has at least the following problems:
when the air flow generated by the impeller passes through the guide vanes, a certain total pressure loss is generated, and the working efficiency of the axial flow fan is reduced. The main reason for the total pressure loss is that the secondary flow is generated when the air flow passes through the guide vane due to the boundary layer of the vane surface and the end wall surface, and the secondary flow loss is generated. In addition, under the action of the secondary flow, the air flow is collected in an included angle area between the root of the guide vane and the end wall surface, and total pressure loss is also generated.
Disclosure of Invention
In view of the defects in the prior art, the technical problem to be solved by the invention is to provide a method for reducing the total pressure loss of the guide vane of the axial flow fan by using the splitter vane, wherein the splitter vane is used for controlling the flow of secondary flow, so that the total pressure loss of the existing guide vane is reduced, and the working efficiency of the axial flow fan is improved.
In order to achieve the purpose, the invention adopts the following technical measures:
a method for reducing total pressure loss of a guide vane of an axial flow fan by using a splitter vane is characterized in that the splitter vane parallel to the guide vane is arranged between the circumferential distances of the guide vane; the splitter blade is positioned at the blade root of the guide blade and connected with a hub of the axial flow fan;
the chord length of the splitter blade is 50% of that of the guide blade, and the height of the splitter blade is less than 10% of that of the guide blade; the mounting angle of the splitter blade should be greater than that of the guide vane, and the difference between the mounting angles of the splitter blade and the guide vane should be less than 10 degrees.
By the aid of the splitter blade, secondary airflow can be reduced, gathering of airflow in an included angle area between the root of the splitter blade and the end wall surface can be reduced, total pressure loss of the splitter blade is reduced, and working efficiency of the axial flow fan is improved.
Further, the distance between the splitter blade and the root of the guide blade closest to the splitter blade is 30 mm.
Preferably, the chord length of the guide vane is 100mm, and the installation angle of the guide vane is 20 degrees. The chord length of the splitter blade is 50mm, and the installation angle of the splitter blade is 28 degrees.
Preferably, the height of the guide vane is 200 mm. The blade height of splitter blade is 2.5mm or 5 mm.
In order to verify the method for reducing the total pressure loss of the guide vane of the axial flow fan by using the splitter vane, the guide vane is exemplified by a commonly-used NACA65 airfoil. The method of the invention was verified by comparing the total pressure loss of the guide vane with splitter vane and the original guide vane (without splitter vane) under different conditions. In the verification example, two splitter blades with different blade heights were selected for comparison.
Compared with the prior art, the invention has the following advantages and beneficial effects:
the method of the invention achieves the purpose of reducing the total pressure loss of the guide vane by arranging the splitter vane parallel to the guide vane between the circumferential distances of the guide vane. The principle is mainly embodied in two aspects: the splitter blade can weaken the strength of secondary flow generated when airflow passes through the guide blade, and the total pressure loss generated by the secondary flow is reduced; and secondly, the separated airflow generated when the airflow passes through the splitter blade can blow off the airflow gathered in the included angle area between the root of the guide vane and the end wall surface, so that the gathering of the airflow in the included angle area between the root of the vane and the end wall surface is reduced, and the total pressure loss is reduced. The invention can reduce the generation of secondary airflow by utilizing the splitter blade, and can reduce the aggregation of airflow in the included angle area between the root part of the guide blade and the end wall surface, thereby finally achieving the purposes of reducing the total pressure loss of the guide blade and improving the working efficiency of the axial flow fan.
Drawings
In order to more clearly illustrate the method of reducing the pressure loss of the guide vane using the splitter vane of the present invention, the method of the present invention was verified by some examples. The drawings that are required to be used in the description of the examples are briefly described below.
FIG. 1 is a schematic cross-sectional view of an original guide vane of an example of the invention;
FIG. 2 is a schematic cross-sectional view of an original guide vane of an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of a new form 1 of an embodiment of the invention;
FIG. 4 is a schematic view of a section of a new form 1 of an example of the invention;
FIG. 5 is a schematic cross-sectional view of a new blade form 2 of an embodiment of the present invention;
FIG. 6 is a schematic view of the profile of the new form 2 of the example of the invention;
FIG. 7 is a graph showing a comparison of the total pressure loss coefficients of the original guide vane (without splitter vane) and the guide vanes with splitter vanes of two different vane heights (new blade form 1 and new blade form 2) in this example;
FIG. 8 is a schematic view of the connection of guide and splitter blades to a hub according to an embodiment of the present invention.
Detailed Description
Example 1
As shown in fig. 1, the original guide vane is not provided with splitter vanes, the guide vane 10 is a NACA65 vane, the chord length L thereof is 100mm, the installation angle is 20 degrees, and the grid pitch T between the guide vanes is 100 mm. As shown in fig. 2, the guide vane 10 has a vane height H of 200 mm.
As shown in fig. 3, the guide vanes 10 are NACA65 vanes, and have a chord length L of 100mm, a setting angle of 20 degrees, and a pitch T of 100 mm. A splitter blade 20 parallel to the guide blade 10 is arranged between the circumferential distances of the guide blade 10, the splitter blade 20 is an NACA65 blade, the chord length L1 of the splitter blade is 50mm, the installation angle is 28 degrees, and the distance A between the splitter blade 20 and the root of the guide blade 10 closest to the splitter blade is 30 mm. As shown in fig. 4, the guide vane 10 has a vane height H of 200 mm. The splitter blade 20 has a blade height H1 of 2.5mm, and as shown in fig. 8, the splitter blade 20 is located at the root of the guide blade 10 and connected to the hub 30 of the axial flow fan.
Example 2
As shown in fig. 5, the guide vanes 10 are NACA65 vanes, and have a chord length L of 100mm, a setting angle of 20 degrees, and a pitch T of 100 mm. A splitter blade 20 parallel to the guide blade 10 is arranged between the circumferential distances of the guide blade 10, the splitter blade 20 is an NACA65 blade, the chord length L1 of the splitter blade is 50mm, the installation angle is 28 degrees, and the distance A between the splitter blade 20 and the root of the guide blade 10 closest to the splitter blade is 30 mm. As shown in fig. 6, the guide vane 10 has a vane height H of 200 mm. The height H1 of the splitter blade 20 is 5 mm. As shown in fig. 8, the splitter blade 20 is located at the root of the guide blade 10 and connected to the hub 30 of the axial flow fan.
As shown in fig. 7, in order to verify the total pressure loss coefficients of the original guide vane (without splitter vane) and the guide vanes (new blade type 1 and new blade type 2) with two different vane heights in the example. The total pressure loss coefficient in the figure is a result of numerical simulation performed under the conditions of a reynolds number of 200000 and an incident angle of 26 ° to 41 °. The results show that the total pressure loss coefficients of the guide vanes with splitter blades (new blade type 1 and new blade type 2) are lower than that of the original guide vanes (without splitter blades).
The total pressure loss coefficients of the original guide vane (without splitter vane) and the guide vanes with splitter vanes of two different vane heights (new profile 1 and new profile 2) were compared in the example of the inventive method. The results show that the total pressure loss coefficient of the guide vane with splitter vane is lower than that of the guide vane without splitter vane. Therefore, the method for reducing the total pressure loss of the guide vane of the axial flow fan by using the splitter vane can effectively achieve the purpose of reducing the total pressure loss of the guide vane of the axial flow fan.
The above description is only an embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can understand that the modifications or substitutions within the technical scope of the present invention should be included in the scope of the present invention.
Claims (6)
1. A method for reducing total pressure loss of a guide vane of an axial flow fan by using a splitter vane is characterized by comprising the following steps of: a splitter blade parallel to the guide blades is arranged between the circumferential distances of the guide blades; the splitter blade is positioned at the blade root of the guide blade and connected with a hub of the axial flow fan;
the chord length of the splitter blade is 50% of that of the guide blade, and the height of the splitter blade is less than 10% of that of the guide blade; the mounting angle of the splitter blade is larger than that of the guide blade, and the difference between the mounting angles of the splitter blade and the guide blade is smaller than 10 degrees.
2. The method for reducing the total pressure loss of the guide vane of the axial flow fan by using the splitter vane as claimed in claim 1, wherein the method comprises the following steps: the distance between the splitter blade and the root of the guide blade closest to the splitter blade is 30 mm.
3. The method for reducing the total pressure loss of the guide vane of the axial flow fan by using the splitter vane as claimed in claim 1, wherein the method comprises the following steps: the chord length of the guide vane is 100mm, and the installation angle of the guide vane is 20 degrees.
4. The method for reducing the total pressure loss of the guide vane of the axial flow fan by using the splitter vane as claimed in claim 1 or 3, wherein: the chord length of the splitter blade is 50mm, and the installation angle of the splitter blade is 28 degrees.
5. The method for reducing the total pressure loss of the guide vane of the axial flow fan by using the splitter vane as claimed in claim 1, wherein the method comprises the following steps: the height of the guide vane is 200 mm.
6. The method for reducing the total pressure loss of the guide vane of the axial flow fan by using the splitter vane as claimed in claim 1 or 5, wherein: the blade height of splitter blade is 2.5mm or 5 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911024721.5A CN110701111B (en) | 2019-10-25 | 2019-10-25 | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911024721.5A CN110701111B (en) | 2019-10-25 | 2019-10-25 | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110701111A true CN110701111A (en) | 2020-01-17 |
| CN110701111B CN110701111B (en) | 2021-02-09 |
Family
ID=69203457
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911024721.5A Active CN110701111B (en) | 2019-10-25 | 2019-10-25 | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110701111B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114962342A (en) * | 2022-05-27 | 2022-08-30 | 哈尔滨工程大学 | Compressor tip area vibration structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101158362A (en) * | 2007-11-29 | 2008-04-09 | 北京航空航天大学 | Big and small blade tandem blade cascade impeller and compressor |
| US20130280060A1 (en) * | 2012-04-23 | 2013-10-24 | Shakeel Nasir | Compressor diffuser having vanes with variable cross-sections |
| CN105736461A (en) * | 2014-12-29 | 2016-07-06 | 通用电气公司 | Axial compressor rotor incorporating splitter blades |
| CN105864105A (en) * | 2016-04-25 | 2016-08-17 | 西北工业大学 | Axial flow compressor stator with in-vitro small blades in hub corner area |
| CN106762824A (en) * | 2016-12-07 | 2017-05-31 | 浙江理工大学 | Axial flow blower 3 d impeller with leaf vein texture and sea-gull type splitterr vanes |
| CN107152419A (en) * | 2017-07-24 | 2017-09-12 | 北京航空航天大学 | A kind of big bending angle compressor stator blade of root series connection multistage blade profile |
-
2019
- 2019-10-25 CN CN201911024721.5A patent/CN110701111B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101158362A (en) * | 2007-11-29 | 2008-04-09 | 北京航空航天大学 | Big and small blade tandem blade cascade impeller and compressor |
| US20130280060A1 (en) * | 2012-04-23 | 2013-10-24 | Shakeel Nasir | Compressor diffuser having vanes with variable cross-sections |
| CN105736461A (en) * | 2014-12-29 | 2016-07-06 | 通用电气公司 | Axial compressor rotor incorporating splitter blades |
| CN105864105A (en) * | 2016-04-25 | 2016-08-17 | 西北工业大学 | Axial flow compressor stator with in-vitro small blades in hub corner area |
| CN106762824A (en) * | 2016-12-07 | 2017-05-31 | 浙江理工大学 | Axial flow blower 3 d impeller with leaf vein texture and sea-gull type splitterr vanes |
| CN107152419A (en) * | 2017-07-24 | 2017-09-12 | 北京航空航天大学 | A kind of big bending angle compressor stator blade of root series connection multistage blade profile |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114962342A (en) * | 2022-05-27 | 2022-08-30 | 哈尔滨工程大学 | Compressor tip area vibration structure |
| CN114962342B (en) * | 2022-05-27 | 2024-04-02 | 哈尔滨工程大学 | Compressor end region vibration structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110701111B (en) | 2021-02-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| DK2736805T3 (en) | Wind turbine blade including vortex generators | |
| EP3037656B1 (en) | Rotor blade with vortex generators | |
| EP2204578A2 (en) | Partial arc shroud for wind turbine blades | |
| CN103422912A (en) | Turbine with moving blades with pits at blade tops | |
| CN112483439B (en) | High-pressure fan | |
| CN109578085B (en) | Method for weakening unsteady acting force of turbine movable blade through guide blade inclination | |
| CN103807201A (en) | Combined suction layout method for controlling compressor stator corner separation | |
| CN111734577B (en) | Slit type wind turbine blade device and slit method | |
| CN109690072B (en) | Wind turbine rotor blade | |
| US20130156593A1 (en) | System and method for root loss reduction in wind turbine blades | |
| CN110701111B (en) | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane | |
| US20110211952A1 (en) | Rotor blade for wind turbine | |
| CN102889237B (en) | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor | |
| CN205422837U (en) | Become turbine how much with moving vane front portion whirlpool pore structure that disappears | |
| CN111577531A (en) | Shark gill type blade drag reduction structure for wind driven generator, blade and manufacturing method | |
| CN106949021A (en) | It is a kind of that the pneumatic equipment bladess of stalling characteristics are improved based on Fractal optimization | |
| CN204692190U (en) | A kind of vane diffuser with deviated splitter vane | |
| CN212360302U (en) | Guide vane of axial flow fan and axial flow fan | |
| CN102278272B (en) | Prominent type Blades For Horizontal Axis Wind before a kind of | |
| CN110242476B (en) | Ultra-low specific speed diagonal flow type water turbine runner | |
| CN112283160B (en) | Compressor rotor blade and design method thereof | |
| CN203939528U (en) | A kind of rotor blade with leaf top cascade structure that improves gas turbine aeroperformance | |
| CN110566400B (en) | Horizontal shaft wind turbine blade | |
| CN108953222B (en) | Centrifugal impeller | |
| CN114201841A (en) | Blade design method and blade for wind generating set |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |